
%% Saturn
warning off
clc;clear;
format longg
options_negx = odeset('RelTol',1e-13,'AbsTol',1e-13,'Events',@NegXcrossing);
options=odeset('RelTol',1e-13,'AbsTol',1e-13);
options_fmincon = optimoptions('fmincon', 'MaxFunctionEvaluations', 5000, ...
    'MaxIterations', 5000,'ConstraintTolerance',1e-6,'Algorithm','Interior-point','stepTolerance',1e-21);
%% Inputs.
G           = 6.674e-11 * ((1/1000)^3); % Gravitational parameters

mass_central = 1.989e30;
%[] Mass of central planet

mass_moon = 5.972e24;         %Callisto
%[] mass of moons

DU = 151.73e6;           %Callisto
%[km] Semi-major axis of Moons, used as distance units for each CRTBP
%environment.

moonName = {'Luna'};
%[] Name of the Moons

thetao = 0;
%[] Initial position of the moon relative to the first point of aries

GM_central = mass_central*G;
%[] Gravitational parameters

GM_moon = mass_moon*G;
%[] Gravitational parameters

N = length(mass_moon);
%[] Number of Moons

u = zeros(N,1);
for ii = 1:N
    u(ii) = GM_moon(ii)/(GM_moon(ii)+GM_central);
end
%[] Gravataional ratio

TU = zeros(N,1);
VU = zeros(N,1);
for ii = 1:N
    TU(ii) = sqrt(DU(ii)^3/GM_central);
    VU(ii) = DU(ii)/TU(ii);
end
%[] Time constant for each crtbp system

theta_dot = zeros(1,N);
for ii = 1:length(theta_dot)
    theta_dot(ii) = sqrt(GM_central*DU(ii))/DU(ii)^2;
end
%[] Theta dot for each planet.




%% environment settings 
dt = 0.01;
startphase=0; % changing the starting position of the periodic
% orbit to show changes in the pole visibility based on the Satellite's position wrt the Sun's pole
% OpenCRTBP_u(u)
%% Define inertial frame FNs
[xs,ys,zs] = ellipsoid(-0,0,0,696340,696340,696340,500);
figure;
s = surface(xs,ys,zs);
rotate(s, [1 0 0], 7.25);
rotate(s, [0 0 1], 73.67+0.014*(2023-1850));
InclinationRotationAngle = 7.25;
RAANRotationAngle = 73.67+0.014*(2023-1850);
PoleDirection = Rotation([0;0;1],RAANRotationAngle,'Degrees')*...
                Rotation([1;0;0],InclinationRotationAngle,'Degrees')*...
                [0;0;1];
rotate(s, PoleDirection, 0);

FN_i = s.VertexNormals;
%%
load('SE_L4_Vertical.mat');
inc_list = zeros(1,length(T_L4_VL));
for ii = 1:length(T_L4_VL)
    IC = IC_L4_VL(:,ii);
    T = T_L4_VL(ii);
    [t,S] = ode113(@(t,S)CR3BP_n(t,S,u),[0:dt:T],IC,options);
    S = S';

    S_i = zeros(size(S));
    S_i = C2I_primary(S(:,ii),u,DU,VU,t(ii)+5.1+startphase);
    COE_list = State2Coe(S_i,GM_central);
    inc_list(ii) = COE_list(3);
end


%% Simulation paramters %%
CameraAngleCapability=60;
inc_desired = 14.5;
optval = min(abs(inc_list-inc_desired));
[ind_opt] = find(abs(inc_list-inc_desired)==optval);

%%
IC_L4 = IC_L4_VL(:,ind_opt);
T_L4 = 2*pi;
IC_L5 = [IC_L4(1);-IC_L4(2);0;...
         -IC_L4(4);IC_L4(5);IC_L4(6)];

OpenCRTBP_u(u); hold on
L4= DetermineOptimalL4andL5State(IC_L4,T_L4,u,DU,VU,TU,dt);
L5= DetermineOptimalL4andL5State(IC_L5,T_L4,u,DU,VU,TU,dt);
load('SEL1_Lyapunov.mat');

size = 1;

[t,S] = ode113(@(t,S)CR3BP_n(t,S,u),[0:dt:2*pi],IC(:,size),options);
S=S';
S_i = zeros(6,length(t));
for ii = 1:length(t)
    S_i(:,ii) = C2I_primary(S(:,ii),u,DU,VU,t(ii));
    epoch(ii) = datetime(2023,1,1,0,0,0) + seconds(t(ii)*TU);
end
L1.S_i = S_i;
L1.epoch = epoch;

%%
% close all
for ii = [1,4,7,11]
epoch = ii; % <Jan : 1, Dec : 12>

PlotSynergy_L145_limb_2(L1,L4,L5,epoch,FN_i,CameraAngleCapability,DU,VU,TU)
% figName = sprintf('Coverage_0inc_%d_temp.jpg',ii);
% exportgraphics(gcf,figName)
% close all

% [~,coveragePercentage(ii)]=PlotSynergy_L145_limb_Apex(L1,L4,L5,epoch,FN_i,CameraAngleCapability,DU,VU,TU,10000);
% figName = sprintf('Coverage_Steroscopic_0inc_%d.eps',ii);
% exportgraphics(gcf,figName)
% close all
end
%%